CN106460558A - Apparatus and method for sealing turbine assembly - Google Patents
Apparatus and method for sealing turbine assembly Download PDFInfo
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- CN106460558A CN106460558A CN201480077800.1A CN201480077800A CN106460558A CN 106460558 A CN106460558 A CN 106460558A CN 201480077800 A CN201480077800 A CN 201480077800A CN 106460558 A CN106460558 A CN 106460558A
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- defiber
- female
- ledge
- turbine
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- 238000007789 sealing Methods 0.000 title claims abstract description 51
- 238000000034 method Methods 0.000 title claims abstract description 8
- 230000009467 reduction Effects 0.000 claims description 8
- 239000012530 fluid Substances 0.000 claims description 7
- 238000005452 bending Methods 0.000 claims description 2
- 230000008859 change Effects 0.000 description 13
- 238000004519 manufacturing process Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 238000010276 construction Methods 0.000 description 5
- 238000001816 cooling Methods 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000000295 complement effect Effects 0.000 description 3
- 229910000975 Carbon steel Inorganic materials 0.000 description 2
- 239000010962 carbon steel Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 235000013399 edible fruits Nutrition 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 241000251468 Actinopterygii Species 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000012809 cooling fluid Substances 0.000 description 1
- 230000000994 depressogenic effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/55—Seals
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to an apparatus and method for sealing a turbine assembly. According to the invention, a turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.
Description
Technical field
Subject matter disclosed herein is related to equipment and the method for black box.Especially, equipment and method are related to along turbine
Defiber between two components of assembly provides sealing member.
Background technology
Due to being such as simple to manufacture or safeguarding the consideration of needs, the component of power plant arrangement can be divided into sub- component, with
Removable mode is connected to each other by them.Position that is closer to each other in sub- component or contacting and can be separated from each other forms so-called
Defiber, and it may include the sealing member being arranged between each component.When there is the pressure reduction relevant with sub- component, that is, from inside
To outside pressure reduction, from the pressure reduction of external-to-internal, or during pressure reduction in sub- component, if defiber do not obtain fully close
If envelope, pressure reduction may trend towards producing the stream through defiber.
As fruit component runs into temperature change or thermograde at work, then sealing is provided possibly to have on defiber
Challenge.For example, as fruit component has the operating temperature of hundreds of degrees Fahrenheit or even thousand of degrees Fahrenheits, then reach in sub- component
During to operating temperature, sub- component can experience sizable thermal expansion.This can cause the change in size along defiber, and in son
When component is transitioned into operating temperature, such change in size can damage the characteristic of any sealing member along defiber.Even if one
The sub- component of denier reaches steady statue or semisteady-state operating temperature, along defiber thermograde also can make sealing member along
Thermograde has different sealing characteristics.Even if the small size change along defiber may also lead to sealing property and has quite greatly
Change so that sealing member becomes uncertain because the change in size of sealing member may make prediction component where connect each other
Touch, and/or component where contact seals is difficult.
Different sealing member characteristics is probably especially to obtain paying close attention in the turbine of efficiency particular importance.For example, although
Leakage can be solved or even desirable, but leakage can be modeled or predict for control or measurement whirlpool
The performance of wheel is useful.The particular elements that may include this defiber and/or sealing member are bubblers in turbine.
Content of the invention
For sealing the equipment of turbine assembly described herein and each side of method to associated with the prior art one
Individual or multiple problem or shortcoming provide solution.
At an exemplary but non-limiting aspect, it relates to a kind of turbine system, including：Compressor section；Combustion
Burn section；Turbine；Bubbler, it has defiber between two components of bubbler；And the sealing along defiber
Part.Sealing member includes ledge, female and the flexible portion between ledge and female.When perpendicular to point
When seeing offline, flexible portion has crooked cross section.The outer surface of crooked cross section contacts the inner surface of female, and curved
The inner surface of bent cross section contacts the outer surface of ledge.
At another exemplary but non-limiting aspect, it relates to a kind of power device, including：Turbine system；Machine
Tool load or electrical load；Entrance system；And control system.Turbine system includes：Compressor section；Burning block；Turbine
Section；Bubbler, it has defiber between two components of bubbler；And the sealing member along defiber.Sealing member bag
Include ledge, female and the flexible portion between ledge and female.When seeing perpendicular to defiber, soft
Property part there is crooked cross section, the outer surface of crooked cross section contacts the inner surface of female, and crooked cross section
Inner surface contacts the outer surface of ledge.
At another exemplary but non-limiting aspect, it relates to a kind of turbine, including the first diffuser element；The
Two diffuser element；Defiber between the first diffuser element and the second diffuser element；And it is close along defiber
Sealing.Sealing member includes male portion, concave portions and the flexible part between male portion and concave portions on cross section
Point.When seeing perpendicular to defiber, flexible portion has crooked cross section, and crooked cross section has fixing end and free end, curved
The outer surface of bent cross section contacts the inner surface of concave portions near free end, and the inner surface of crooked cross section is being fixed
End nearby contacts the outer surface of male portion.
Brief description
Fig. 1 is the schematic diagram of turbine engine system；
Fig. 2 is the partial cross-section of the bubbler in turbine engine system；
Fig. 3 A is the detailed view of the defiber in two Components Matching positions of bubbler and associated sealing member；
Fig. 3 B is the detailed view of a part of Fig. 3 A；
Fig. 4 is the cross-sectional view of defiber between diffuser element and sealing member；And
Fig. 5 is the separate views of the flexible member of sealing member.
Specific embodiment
One or more specific embodiments of the invention will be described below.In order to be devoted to providing to these enforcements
The actual all features realized may be described by the simple and clear description of example in the description.It should be appreciated that ought for example exist
Develop in any engineering or design object any this actual to come it is necessary to make many proprietary decisions for realizing when realizing
Realize the objectives of developer, for example meet with system about and with the relevant constraint of business, the objectives of developer
Can be changed each other according to different realizations.Moreover, it will be appreciated that this development is probably complicated and time-consuming, but
Even so, for having the those of ordinary skill of benefit of the disclosure, this development will be design, and produce and manufacture
Routine mission.
Disclosed herein is detailed example embodiment.But, concrete structure disclosed herein and function detail are only generation
Table, so that description example embodiment.But, embodiment of the disclosure can be presented as many alterative version, and should not manage
Solve as being confined to embodiment set forth herein.
Therefore although example embodiment can have various modifications and alterative version, but only show in an illustrative manner in figure
Go out embodiment, and embodiment will be described herein in detail.But it is to be understood that, it is not meant to example embodiment office
It is limited to disclosed particular form, but on the contrary, example embodiment covers all modifications falling within the scope of this disclosure, equivalent
And alternative.
Term used herein is merely to describe specific embodiment, and is not meant to limit example embodiment.As herein
Used, singulative "a", "an" and "the" is intended to also include plural form, unless the context clearly dictates otherwise.
As use alpha nerein, term " inclusion " and/or "comprising" define the feature that presence stated, integer, step, operation,
Element and/or component, but do not preclude the presence or addition of one or more of the other feature, integer, step, operation, element, component
And/or combinations thereof.
Although term first, second, main, auxiliary etc. can be used for herein describing various elements, these elements should not
Limited by these terms.These terms are used merely to distinguish an element and another element.Such as (but not limited to), first yuan
Part can be described as the second element, and similarly, the second element can be described as the first element, without departing from the scope of example embodiment.
As used herein, term "and/or" includes any and all combination of one or more associated Listed Items.
Can just for the sake of helping reader, and be should not be construed as limiting the present invention's using some terms herein
Scope.For example, " on ", D score, " level ", " vertical ", " upstream ", " downstream ", the word such as "front", "rear" figure is only described
The construction of middle display.In fact, the element of embodiment of the disclosure or multiple element can be oriented in any direction, therefore term should
When being interpreted as comprising such modification, unless otherwise prescribed.
As used in the specification and in the claims, " basic " and " about " is at least included with respect to ideal value
Or the deviation within manufacturing tolerance, working tolerances and/or inspection tolerance of nominal value.
The disclosure can be applicable to compress the various gas-turbine units of suction air, such as (but not limited to) heavy
Type gas turbine；Aviation derives gas turbine etc..Embodiment of the disclosure can be applicable to single gas-turbine unit or many
Individual gas-turbine unit.The gas turbine that embodiment of the disclosure can be applicable to work in single loop or combined cycle is sent out
Motivation.
Fig. 1 illustrates gas-turbine unit 10, and it has entrance system 12.Gas-turbine unit 10 generallys include compression
Machine 14, at least one burner with combustor 16 and turbine 18.In the gas turbine based on land, turbine
18 typically drive mechanical load or electrical load, such as electromotor 20.Compressor 14 is provided with entrance, entrance may include multiple enter
Mouth stator (not shown), they are arranged in the downstream of inlet plenum 22.Turbine 18 is fluidly connected on bubbler 100,
Bubbler 100 is connected on heat recovery steam generator 32.Entrance system 12 generallys include rainwater cover 24, and rainwater cover 24 is installed to
On 26 upstream end between ingress filtering.Rainwater cover 24 is fluidly connected on inlet plenum 22 by intake air conduit 28.Can
Control system 30 is provided to control any aspect of gas-turbine unit 10.Gas-turbine unit 10 may be mounted to power dress
The part put.
Fig. 2 illustrates the simplification partial cross-section of the bubbler 100 in gas-turbine unit 10.The inside of bubbler 100
Part 102 allows bubbler 100 that rate conversion is become pressure, i.e. execute diffusion to the gas stream in gas-turbine unit 10
Function.The exterior section 104 of bubbler 100 provides the region for cooling stream 106.Cooling stream 106 is provided to be in order that shell
107 keep below maximum operating temperature.For example, shell 107 can be fabricated by by carbon steel, and carbon steel has about 600 to 700 Fahrenheits
The highest of degree allows operating temperature, and interior section 102 may have about the high-temperature combustion gas of 1200 degrees Fahrenheits.Can provide cold
But 106 are flowed, to allow shell 107 to work under such working condition.
Fluid (for example, cooling down stream 106) in exterior section 104 (for example, burns than the fluid in interior section 102
Gas) it is in higher pressure.For example, the fluid in exterior section 104 can have higher than the fluid in interior section 102
Pressure between 2psi and 3psi.This pressure reduction will make fluid from outside part 104 flow to interior section 102.In fact, having a mind to
Some streams are provided at front tap 110 and rear tap 112.
Fig. 3 A provides the view of the outer surface towards bubbler shell 108.As shown, bubbler shell 108
Including first component 114 (upper component) and second component 116 (lower member), they are combined formation shell, and hull shape becomes to expand
The periphery of scattered device 100.Any amount of component can be provided.In order to simple, describe two components.Two components can be each basic
For bubbler 100 180 °.
First component 114 and second component 116 meet at defiber 118, and defiber 118 extends through bubbler 108
Reach exterior section 104, and generally along axial direction or the axially stream direction extension of gas-turbine unit 10.Show
Defiber 118 is basic horizontal, but this should not be construed as restricted.The defiber of any construction is applicable, bag
Include and be for example circumferentially separated line, vertical defiber, horizontal separation line, non-straight defiber or combinations thereof.Close due to being formed
The reason component of sealing assembly 120, the major part of defiber 118 is sightless in figure 3 a.
Fig. 3 B shows the zoomed-in view of Fig. 3 A, and illustrates a part for black box 120.Fig. 3 A particularly illustrates two
Black box 120, they are essentially identical and recline end-to-end each other.
Fig. 4 illustrates the cross section of black box 120.Black box 120 includes the protuberance being inserted in female 124
Divide 122.Show the flexible portion 126 between ledge 122 and female 124.Ledge 122 and female
124 can be formed on two parts, and two parts are substantially mirrored into each other and form circumferential shell.Ledge 122 and depressed part
Divide 124 can be formed by any suitable material.Flexible portion 126 can be by the enough elasticity of offer and/or the work as spring
With any suitable material make.
Ledge 122 may include outer surface 128, and outer surface 128 can be convex and/or substantially V-shaped.Female
124 can be spill and/or general U-shape and/or fish mouth shaped.Ledge 122 can be tab, and female 124 can be then recessed
Groove.In fact, ledge 122 and female 124 can have any of other side that is complimentary to one another and adapting to the disclosure
Shape.Gap 130 is provided between ledge 122 and female 124.Gap 130 can allow ledge 122 and depression
There is manufacturing tolerance between part 124.Gap 130 can allow to be had due to thermal expansion between ledge 122 and female 124
Change, as discussed above.Thermal expansion is possibly due to what the radial thermal expansion of such as bubbler 100 caused.Outer surface
128 can be substantially complementary with the inner surface of flexible portion 126.Gap 130 can be for providing for the chi manufacturing and/or heat load causes
Any distance in sufficient space for very little change.In this example, gap 130 is substantially between 0 inch and 0.1 inch.?
In example, gap 130 is substantially between 0.020 inch and 0.080 inch.In this example, gap 130 is substantially between 0.040
Between inch and 0.060 inch.With ledge 122 and female 124 thermal expansion, gap 130 can diminish or become big, this
Factor depending on such as ad hoc structure construction and/or thermograde.
Black box 120 can be not provided with flexible portion 126.This construction provides better than not including ledge 122 and recessed
The advantage of the defiber 118 (" straight " defiber) of sunken part 124, because the complementary structure of ledge 122 and female 124
Making permission has some change in size because of thermal expansion, or has change in size, simultaneously still to " pen because of other reason
Directly " defiber provides good sealing property, because the complementary shape of ledge 122 and female 124 allows hot swollen
Swollen and shrink during at least to a certain extent between ledge 122 and female 124 retain contact.
Flexible portion 126 has crooked cross section, and it can be essentially V-arrangement or U-shaped.The first end 132 of flexible portion 126 can
Contact the outer surface of ledge 122 at least at a point, and first end 132 is shown as completely along ledge
122 the first side 134 contact ledge towards interior section 102.Flexible portion 126 can be protected by any suitable means
Hold in place.As shown in Figure 4, flexible portion 126 is clipped in ledge 122 and female 124 at the first side 134
Between so that ledge 122 both contacts flexible portion 126 with female 124.Also show flexible portion 126 to set
Put in the notch in ledge 122 or groove 136.Groove 136 can provide the tight fit of opposing flexible portion 126 movement
(being such as press-fitted), or the lax cooperation allowing flexible portion 126 to slide in groove 136 can be provided.
Although outer surface 128 and flexible portion 126 have similar shape, flexible portion 126 can be larger V-arrangement or U
Shape is so that when first end 132 is constrained as described above, the second end 138 is biased away from the face of ledge 122
The second side 140 to exterior section 104.Second end 138 can contact the inner surface of female 124.With regard to this construction, flexible
Part 126 crosses over gap 130, and when applying pressure reduction through defiber 118 from exterior section 104 to interior section 102, permits
Permitted the preferably stream by defiber 118 for the opposing.During due to applying pressure, pressure application trends towards opening flexible portion 126
V-arrangement or U-shaped or make it flatten, or the power of the state trending towards promoting flexible portion 126 to enter " less bending ", and
Improve sealing.And, by contacting ledge 122 and female 124, flexible portion with shown by way of description
126 can bend in the case that there is change in size in gap 130 due to manufacture and/or thermal expansion.
Due to including flexible portion 126, in inner surface and/or the ledge of flexible portion 126 and female 124
The gap producing between 122 outer surface can be 0.0 to 0.004 inch, 0.0 to 0.002 inch, or 0.0 to 0.1 inch, or
Person provides sufficiently sealed any gap.Flexible portion 126 is flexible, expand and/or compress, farthest to subtract as far as possible
The gap of little generation.
There is provided some advantages including flexible portion 126, because black box 120 becomes the sealing than no flexible portion 126
Assembly has more definitiveness.For example, the period that flexible portion 126 leads to its change in thermal expansion expands and shrinks (by deformation)
Ability allow have more consistent sealing along defiber 118.Without flexible portion 126, the energy of black box 120 sealing
Power becomes less measurable and/or less reliable.For example, if black box 120 at a higher temperature can not be effective
Ground sealing, then, due to due to pressure, more fluid will flow through defiber 118.This can to the combined cycle efficiency of turbine
There is undesirable impact, because for example entering in bubbler 100 than the more cooling fluids needing, and reducing joint
Cycle efficieny.Because sealing is improved, may occur in which and such as reduce cooling stream, the uncertainty of minimizing stream prediction and improve heat in advance
The benefit surveyed.
The separately shown flexible portion of Fig. 5 126.Separately shown flexible portion 126 more easily shows the blade 142 of extension,
Or may be provided at the extension of the crooked cross section of flexible portion on one or two end of flexible portion 126.
Return to Fig. 3 B, the blade 142 of extension may be provided at the position wherein eliminating ledge 122 and female 124
Put.Consider due to for example manufacturing and/or safeguarding, recline end-to-end each other in the black box 120 of two basic simlarity
Ledge 122 and the length of female 124 can be omitted in position.And, the position terminated in single black box 120, can
Omit ledge 122 and female 124.In these cases, it is possible to provide the blade 142 of extension is guaranteeing flexible portion
126 fully extend to cover defiber 118.As can be seen in the diagram, in the position not including the blade 142 extending
Put (near the second end 138 in this drawing), defiber 118 is not covered by compliant member.Including ledge 122 and recessed
The position of sunken part 124, omitting the blade 142 extending can prevent from disturbing, and still allow for integral sealing simultaneously, do not having protuberance
In the case of dividing 122 and female 124, the blade 142 of extension will not cause interference, but cover defiber 118 and formed close
Envelope.
Although on the defiber concentrating on bubbler described above, black box 120 can be applicable to there is defiber
Any component.Additionally, defiber can be straight or curved, and be applicable to any sealing member, and due to component it
Between relative motion (for example, the thermal expansion of component) and occur change situation in be useful especially.
Although already in connection with it is now recognized that most practical and preferred embodiment to describe the present invention, it will be appreciated that
It is that the present invention is not limited to disclosed embodiment, but on the contrary, the present invention is intended to cover including the spirit in claims
With within the scope of various modifications and equivalent arrangements.
List of parts
10 gas-turbine units
12 entrance systems
14 compressors
16 combustor
18 turbines
20 electromotors
22 inlet plenum
24 rainwater covers
Between 26 ingress filterings
28 intake air conduits
30 control systems
32 heat recovery steam generators
100 bubblers
102 interior sections
104 exterior sections
106 cooling streams
107 shells
108 bubbler shells
Tap before 110
Tap after 112
114 first components
116 second components
118 defibers
120 black boies
122 ledges
124 females
126 flexible portions
128 outer surfaces
130 gaps
132 first ends
134 first sides
136 grooves
138 second ends
140 second sides
142 blades.
Claims (20)
1. a kind of turbine system, including：
Compressor section；
Burning block；
Turbine；
Bubbler, it has defiber between two components of described bubbler；And
Along the sealing member of described defiber, wherein, described sealing member includes
Ledge,
Female, and
Flexible portion between described ledge and described female, wherein：
When seeing perpendicular to described defiber, described flexible portion has crooked cross section,
The outer surface of described crooked cross section contacts the inner surface of described female, and
The inner surface of described crooked cross section contacts the outer surface of described ledge.
2. turbine system according to claim 1 it is characterised in that described defiber along described bubbler axial direction side
To.
3. turbine system according to claim 1 is it is characterised in that the inner surface of described female is generally U-shaped.
4. turbine system according to claim 1 is it is characterised in that described crooked cross section is essentially V-arrangement.
5. turbine system according to claim 1 it is characterised in that the outer surface of described ledge a part of basic
For V-arrangement.
6. turbine system according to claim 1 is it is characterised in that described ledge is in described female
, there is space in portion between described ledge and described female, to allow them relative to each other to move due to thermal expansion
Dynamic.
7. turbine system according to claim 6 is it is characterised in that described thermal expansion is the expanded radially of described bubbler
Cause.
8. turbine system according to claim 1 is it is characterised in that described flexible portion seals described ledge and institute
State the space between female.
9. turbine system according to claim 1 is it is characterised in that described crooked cross section is arranged so that leap is described
The pressure reduction of defiber trends towards making the state of described crooked cross section court less bending open.
10. turbine system according to claim 1 is it is characterised in that described turbine system further includes the second sealing
Part, described second seal is substantially identical with described sealing member, and wherein, described sealing member and described second seal are along described
Defiber reclines each other end-to-end.
11. turbine systems according to claim 10 it is characterised in that described sealing member and described second seal that
Near this position reclining, described sealing member and described second seal do not include described ledge and described female.
12. turbine systems according to claim 11 are it is characterised in that described flexible portion includes described crooked cross section
Extension so that near described sealing member and described second seal position against each other, described crooked cross section is more
Long, the vicinity of the position of inner surface of the outer surface described female of contact in described crooked cross section for the described extension.
13. turbine systems according to claim 1 are it is characterised in that described sealing member includes saving along described defiber
Omit described female and the length of described ledge, and described flexible portion has included the extension of described crooked cross section
Portion is so that described crooked cross section is longer at the position eliminating described female and described ledge.
14. turbine systems according to claim 1 are it is characterised in that described crooked cross section includes dashing forward with respect to described
The position going out the inner surface that the fixing end partly fixed contacts described female with the outer surface in described crooked cross section is attached
Near free end.
15. turbine systems according to claim 14 are it is characterised in that described sealing member includes saving along described defiber
Omit described female and the length of described ledge, and described flexible portion has included the extension of described crooked cross section
Portion is so that described crooked cross section is longer at the position eliminating described female and described ledge.
A kind of 16. power devices, including：
Turbine system, including
Compressor section,
Burning block,
Turbine,
Bubbler, it has defiber between two components of described bubbler,
Along the sealing member of described defiber, wherein said sealing member includes
Ledge,
Female, and
Flexible portion between described ledge and described female, wherein：
When seeing perpendicular to described defiber, described flexible portion has crooked cross section,
The outer surface of described crooked cross section contacts the inner surface of described female, and
The inner surface of described crooked cross section contacts the outer surface of described ledge；
Mechanical load or electrical load；
Entrance system；And
Control system.
A kind of 17. turbines, including：
First diffuser element；
Second diffuser element；
Defiber between described first diffuser element and described second diffuser element；And
Along the sealing member of described defiber, wherein, described sealing member includes on cross section,
Male portion,
Concave portions, and
Flexible portion between described male portion and described concave portions, wherein：
When seeing perpendicular to described defiber, described flexible portion has crooked cross section,
Described crooked cross section has fixing end and free end,
The outer surface of described crooked cross section contacts the inner surface of described concave portions near described free end, and
The inner surface of described crooked cross section contacts the outer surface of described male portion near described fixing end.
18. turbines according to claim 17 are it is characterised in that described first diffuser element and described second bubbler
Component is collectively forming the shell around the stream by described turbine, is diffused in the inside of described shell by the stream of described turbine,
And described sealing member is suitable to prevent fluid from passing through described defiber to flow to the inside of described shell from the outside of described shell.
19. turbines according to claim 17 it is characterised in that described defiber along described bubbler axial direction stream side
To extension.
The method of the turbine described in a kind of 20. sealing claim 17, methods described includes：
Described flexible portion is arranged between described concave portions and described male portion so that described crooked cross section outer
Surface contacts the inner surface of described concave portions near described free end, and the inner surface of described crooked cross section is described
The outer surface of described male portion is contacted near fixing end；And
Internal pressurization to described first diffuser element and described second diffuser element.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/PL2014/000035 WO2015152742A1 (en) | 2014-04-02 | 2014-04-02 | Apparatus and method for sealing turbine assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106460558A true CN106460558A (en) | 2017-02-22 |
| CN106460558B CN106460558B (en) | 2018-05-15 |
Family
ID=50588782
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480077800.1A Active CN106460558B (en) | 2014-04-02 | 2014-04-02 | For sealing the apparatus and method of turbine assembly |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US10704405B2 (en) |
| JP (1) | JP6659567B2 (en) |
| CN (1) | CN106460558B (en) |
| DE (1) | DE112014006552B4 (en) |
| WO (1) | WO2015152742A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102016223867A1 (en) * | 2016-11-30 | 2018-05-30 | MTU Aero Engines AG | Turbomachinery sealing arrangement |
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|---|---|---|---|---|
| US2352583A (en) * | 1942-10-03 | 1944-06-27 | Westinghouse Electric & Mfg Co | Joint construction |
| US4020971A (en) * | 1974-04-19 | 1977-05-03 | Ostbo John D B | Method of and arrangement for sealing the joints between the parts of a multi-part housing |
| GB2087501A (en) * | 1980-11-14 | 1982-05-26 | United Technologies Corp | Wedge-shaped seal for flanged joints |
| US5076591A (en) * | 1988-12-22 | 1991-12-31 | General Electric Company | Gas leakage seal |
| CN1853032A (en) * | 2003-09-11 | 2006-10-25 | 西门子公司 | Gas turbine and sealing means for a gas turbine |
| WO2008033897A1 (en) * | 2006-09-12 | 2008-03-20 | Parker-Hannifin Corporation | Seal assembly |
| EP2653663A2 (en) * | 2012-04-19 | 2013-10-23 | General Electric Company | Seal for a turbine system |
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| US4503668A (en) | 1983-04-12 | 1985-03-12 | The United States Of America As Represented By The Secretary Of The Air Force | Strutless diffuser for gas turbine engine |
| DE3941089A1 (en) * | 1988-12-22 | 1990-06-28 | Gen Electric | Gas seal for opposing flanges of housing structure - incorporates groove in flange and narrow compressible packing |
| DE4243059C2 (en) | 1992-12-18 | 1994-09-22 | Ferag Ag | Device for trimming flat products, in particular multi-sheet printed products |
| US6971844B2 (en) | 2003-05-29 | 2005-12-06 | General Electric Company | Horizontal joint sealing system for steam turbine diaphragm assemblies |
| JP2007120340A (en) | 2005-10-26 | 2007-05-17 | Mitsubishi Heavy Ind Ltd | Combustor tail pipe seal structure of gas turbine |
| JP2009024631A (en) * | 2007-07-20 | 2009-02-05 | Hitachi Ltd | Gas turbine facility |
| CH703309A1 (en) * | 2010-06-10 | 2011-12-15 | Alstom Technology Ltd | Exhaust housing for a gas turbine and method for producing such an exhaust housing. |
| JP5917311B2 (en) * | 2012-06-19 | 2016-05-11 | 株式会社東芝 | Axial flow turbine |
| EP2961939B1 (en) * | 2013-02-27 | 2019-04-10 | United Technologies Corporation | Assembly for sealing a gap between components of a turbine engine |
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2014
- 2014-04-02 DE DE112014006552.8T patent/DE112014006552B4/en active Active
- 2014-04-02 WO PCT/PL2014/000035 patent/WO2015152742A1/en active Application Filing
- 2014-04-02 JP JP2016559396A patent/JP6659567B2/en active Active
- 2014-04-02 CN CN201480077800.1A patent/CN106460558B/en active Active
- 2014-04-02 US US15/301,659 patent/US10704405B2/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2352583A (en) * | 1942-10-03 | 1944-06-27 | Westinghouse Electric & Mfg Co | Joint construction |
| US4020971A (en) * | 1974-04-19 | 1977-05-03 | Ostbo John D B | Method of and arrangement for sealing the joints between the parts of a multi-part housing |
| GB2087501A (en) * | 1980-11-14 | 1982-05-26 | United Technologies Corp | Wedge-shaped seal for flanged joints |
| US5076591A (en) * | 1988-12-22 | 1991-12-31 | General Electric Company | Gas leakage seal |
| CN1853032A (en) * | 2003-09-11 | 2006-10-25 | 西门子公司 | Gas turbine and sealing means for a gas turbine |
| WO2008033897A1 (en) * | 2006-09-12 | 2008-03-20 | Parker-Hannifin Corporation | Seal assembly |
| EP2653663A2 (en) * | 2012-04-19 | 2013-10-23 | General Electric Company | Seal for a turbine system |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2015152742A1 (en) | 2015-10-08 |
| DE112014006552B4 (en) | 2023-10-05 |
| JP2017519145A (en) | 2017-07-13 |
| US10704405B2 (en) | 2020-07-07 |
| JP6659567B2 (en) | 2020-03-04 |
| US20170114654A1 (en) | 2017-04-27 |
| CN106460558B (en) | 2018-05-15 |
| DE112014006552T5 (en) | 2016-12-29 |
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Effective date of registration: 20231228 Address after: Swiss Baden Patentee after: GENERAL ELECTRIC CO. LTD. Address before: New York State, USA Patentee before: General Electric Co. |